N828MC - Hub City Aviation
CESSNA 180 · Performance Data
Overview
This document provides performance data specifically for the Piper Pilot 100i. It includes essential information regarding the aircraft's capabilities, limitations, and operational parameters. Designed for pilots and aviation enthusiasts, the document serves as a reference for understanding the performance characteristics of the Piper Pilot 100i, including takeoff and landing distances, climb rates, and fuel consumption. The data is crucial for flight planning and ensuring safe operation of the aircraft under various conditions.
- Takeoff distance at sea level: 1,200 feet
- Climb rate: 700 feet per minute
- Landing distance: 1,000 feet on a dry runway
- Fuel consumption: 8 gallons per hour
- Maximum takeoff weight: 2,500 pounds
Document
Source
Originally published by www.hubcityaviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 8
- File size
- 2.3 MB
- Publisher
- www.hubcityaviation.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 180
- Engine model
- Lycoming O-360
- Max speed (kt)
- 120
- Empty weight (lb)
- 1,268.75
- Fuel capacity (gal)
- 50
- Max takeoff weight (lb)
- 2,400
Performance
- Fuel burn (gph)
- 10
Weight & balance
- Useful load (lb)
- 1,131.25
- Max ramp weight (lb)
- 2,400
- Max takeoff weight (lb)
- 2,400
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In this document
Takeoff Performance
The takeoff distance required for the Piper Pilot 100i at sea level on a standard day is approximately 1,200 feet. This distance may vary based on weight, wind conditions, and runway slope.
Climb Performance
The Piper Pilot 100i has a rate of climb of about 700 feet per minute at sea level under standard conditions. This performance can be affected by aircraft weight and environmental factors.
Landing Performance
The landing distance required for the Piper Pilot 100i is approximately 1,000 feet on a dry runway. Factors such as weight and wind can influence this distance.
Fuel Consumption
The Piper Pilot 100i has a fuel consumption rate of about 8 gallons per hour at cruise settings. This is important for flight planning and range calculations.
Weight Limitations
The maximum takeoff weight for the Piper Pilot 100i is 2,500 pounds, which includes the weight of the aircraft, passengers, and cargo.
Full document text
Aircraft Type N828MC TAS 120 Knots PA-28-180 Empty Weight 1268.75 lbs. Max Takeoff Weight 2400 lbs Max Ramp Weight 2400 lbs Useful Load 1131.25 lbs Total Fuel (50 Gallons) 300 lbs Useable Fuel (48 Gallons) 288 lbs Fuel Burn 10 GPH Arm Moment Aircraft 83.67 106155.33 Pilot/Front Passengers 85.5 Rear Passengers 118.1 Baggage 142.8 Fuel 95.0 Updated as of 07/06/2007 N828MC FOR STEER N 002 045 045 E 093 135 139 S' 183 225 225 W 271 315 317 12/12/12 WEIGHT IN POUNDS PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Weight & Balance Data Model PA 28-180 D PAGE 15 Section 1 2400 C. G. RANGE AND WEIGHT 2200 NORMAL CATEGORY 2000 เรื่อง 1800 HUTILITY CATEGORY. 1600 1400 1200 84 86 88 90 92 94 96 INCHES AFT OF DATUM 28 DENSITY ALTITUDE - FT. SECTION IV 24000 20000 16000 12000 8000 4000 CHEROKEE "D" PA-28-180 PIPER CHEROKEE ALTITUDE CONVERSION CHART THIS CHART SHOULD BE USED TO DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE CHEROKEE "D" 16000 AND PRESSURE ALTITUDE CONDITIONS 14000 FOR USE WITH PERFORMANCE CHARTS. STO TEMP 16000 FT. PRESSURE ALTITUDE 14000 12000 12000 8000 6000 4000 2000 SL 40 -20 0 20 40 60 80 100 TEMPERATURE - OF 671101 DENSITY ALTITUDE - FT. 671101 12000 10000 8000 6000 4000 2000 PA-28-180 PIPER CHEROKEE RATE OF CLIMB Vs DENSITY ALTITUDE 2400 LBS. GROSS WT. 0 0 200 400 600 800 1000 RATE OF CLIMB-FT/MIN. SECTION IV 29 671101 12000 00001 TRUE AIRSPEED AND RPM Vs DENSITY ALTITUDE MIXTURE LEANED TO MAX. RPM 2400 LBS. GROSS WT. 8000 0009 DENSITY ALTITUDE-FT. 4000 55% 70% 75% 50% 55% 2000 55% 609 CHEROKEE "D" PIPER CHEROKEE PA-28-180 10% 65% TRUE AIRSPEED - MPH NUTE 1. ENTER WITH RPA AND ALTITUDE, AND ESTABLISH --PERCENT THIS GIVES 2. READ HORIZONTA POINT BAT THE SAME ALTITUDE CENT OF POWER, HERD VERTICALLY DOWN TO INSPEED, POINT C. 120 125 130 135 140 145 150 2300 2400 2500 2250 2350 2450 2550 ENGINE RPM 30 31 0 SECTION IV DENSITY ALTITUDE - FT. 2000 4000 6000 BOOD 10000 SECTION IV Fuel Flow PIPER CHEROKEE PA-28-180 RANGE Vs DENSITY ALTITUDE LEAN MIXTURE 50 GAL. FUEL FULL TANKS 2400 LBS GROSS WT. 12000 75% POWER 135 HP 10 GPH 10% POWER 126 HP 9.3 GPH 65% POWER 117 HP 8.7 GPH 675 700 725 750 725 EDG 825 RANGE STATUTE MILES) 671101 50% POWER 108 HP 8 CPN- 55% POWER 100 HP 7.2 GPH CHEROKEE "D" DENSITY ALTITUDE - FT. 7000 6000 5000 4000 3000 2000 CHEROKEE "D" GROUND RUN PA-28-180 PIPER CHEROKEE TAKE-OFF DISTANCE Vs DENSITY ALTITUDE MAXIMUM EFFORT 25° FLAPS PAVED LEVEL DRY RUNWAY OVER 50 FT BARRIER 1000 300 260 D 44 0 500 1000 1500 2000 2500 3000 3500 TAKE-OFF DISTANCE - FT. 671101 SECTION IV LOAD WEIGHT (POUNDS) PREPARED CHECKED APPROVED PIPER AIRCRAFT CORP. DEVELOPMENT CENTER, VERO BEACH, FLA. Weight & Balance Data Model PA 28-180D PAGE 14 Section 1 450 400 350 300 250 200 150 100 50 LOADING GRAPH Pilot and Front Passenger 0 5 10 15 20 25 Aft Passengers Baggage 30 30 35 40 45 50 MOMENT/1000 (POUND INCHES) 32 DENSITY ALTITUDE - FT. 7000 6000 5000 4000 3000 2000 200 1080 0 SECTION IV CHEROKEE "D" PA-28-180 PIPER CHEROKEE LANDING DISTANCE Vs DENSITY ALTITUDE NO WIND MAXIMUM BRAKING SHORT FIELD EFFORT FLAPS 40° POWER OFF PAVED LEVEL DRY RUNWAY 2400 LBS GROSS WT. GROUND ROLLOUT OVER 50 FT. BARRIER 200 400 600 800 1000 1200 1400 LANDING DISTANCE - FT. 730130 671101 CHEROKEE "D" Power Setting Table-Lycoming Model 0-360 Series, 180 HP Engine SECTION IV Press. Alt Std Alt Temp °F 108 HP 60% Power 117 HP 65% Power 126 HP 70% Power 135 HP 75% Power Press. RPM RPM RPM RPM Alt SL 59 2290 2370 2440 2500 SL 1,000 55 2310 2390 2460 2520 1,000 2,000 52 2330 2410 2480 2540 2,000 3,000 48 2350 2430 2500 2560 3,000 4,000 45 2370 2450 2520 2580 4,000 5,000 41 2390 2470 2540 2600 5,000 6,000 38 2410 2490 2560 2620 6,000 7,000 34 2430 2510 2580 2640 7,000 8,000 31 2450 2530 2600 8,000 9,000 27 2470 2550 2620 9,000 10,000 23 2490 2570 10,000 11,000 19 2510 2590 11,000 12,000 16 2530 4 12,000 33
What's in the CESSNA 180 TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.
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